Ceramic composite thermal protection system

ABSTRACT

An apparatus comprises a thermal protection element, a number of washers, a ceramic layer, a number of blind fasteners, and a number of tabs. The thermal protection element has an upper surface, a lower surface, and a plurality of sides. The ceramic layer covers at least the plurality of sides of the thermal protection element. The number of tabs is connected to the number of sides by the number of blind fasteners secured to the ceramic layers. The tabs may be part of a frame secured to a groove around the plurality of sides.

BACKGROUND INFORMATION

1. Field

The present disclosure relates generally to aerospace vehicles and, inparticular, to a method and apparatus for attaching thermal protectionsystems to an aerospace vehicle.

2. Background

A spacecraft is a type of vehicle or device designed for space flight.When a spacecraft returns to earth, the spacecraft may encounter hightemperatures on reentry. A thermal protection system may cover some oressentially all of a spacecraft. A thermal protection system may protectthe spacecraft from temperatures that may reach around 1650 degreesCelsius during atmospheric reentry. Further, this thermal protectionsystem also may be used to protect the spacecraft from heat and cold inspace while in orbit.

A thermal protection system may have different materials in differentlocations of the spacecraft depending on the amount of heat protectionneeded. For example, reinforced carbon-carbon may be used in the nose orleading wing edges of a spacecraft, such as a space shuttle. Hightemperature reusable surface insulation tiles may be used on theunderside of an aircraft. Flexible insulation blankets, low temperaturereusable surface insulation tiles, and other materials may be used fordifferent locations on the spacecraft. Each type of thermal protectionsystem may have specific heat protection, impact resistance, and weightcharacteristics.

It is desirable to have a thermal protection system that requires littleor no maintenance. Some components used by a thermal protection systemmay include modular components that may be quickly removed and replaced.For example, tiles are examples of components that may be used in athermal protection system. A tile is a thermal protection systemcomponent that may be fabricated from ceramic and/or ceramic matrixcomposite materials. More specifically, a tile may have, for example, aceramic substrate with a ceramic matrix composite layer wrapped aroundthe core. In the event that a tile may need to be replaced, it isdesirable to minimize the amount of time needed to replace tiles on aspacecraft. For example, a vehicle turnaround time of around 48 hours oras little as two hours may be desirable.

Thermal protection systems on existing spacecraft may be adhesivelybonded or mechanically attached. With bonded thermal protection systems,the amount of time and cost associated with installation, inspection,and/or repair may be much greater than compared to a mechanicallyattached system. Further, bonded thermal protection systems are notnecessarily removable without destroying a portion of the part. As aresult, inspection of a spacecraft substructure and/or internalspacecraft subsystems may be time consuming and expensive. Anotherdrawback of bonded thermal protection systems is the temperaturelimitations of the adhesive bond lines.

Mechanical attachments may include, for example, a standoff or a carrierpanel. A standoff thermal protection system may include stiffened panelsencapsulating a back face insulation that is mechanically attachedthrough flanges or metallic standoffs. A carrier panel thermalprotection system may have tiles and/or blankets bonded to metal orcomposite carrier panels that are mechanically attached to a structure.

With mechanically attached thermal protection systems, increased weightmay occur, which is undesirable with space operation vehicles. In somecases, the weight of a carrier panel on which the tile is mounted forattachment to a structure may be a large percentage of the total weightof the thermal protection system.

Therefore, it would be advantageous to have a method and apparatus thattakes into account one or more of the issues discussed above as well aspossibly other issues.

SUMMARY

In one advantageous embodiment, an apparatus comprises a thermalprotection element, a number of washers, a ceramic layer, a number ofblind fasteners, and a number of tabs. The thermal protection elementhas an upper surface, a lower surface, and a plurality of sides. Theceramic layer covers at least the plurality of sides of the thermalprotection element. The number of tabs is connected to the number ofsides by the number of blind fasteners secured to the ceramic layer.

In another advantageous embodiment, an apparatus comprises a thermalprotection element, a groove, and a frame. The thermal protectionelement has an upper surface, a lower surface, and a plurality of sides.The groove is formed in the plurality of sides of the thermal protectionelement. The frame has an inner edge and a number of tabs opposite ofthe inner edge. The inner edge of the frame is secured to the groove.

In yet another advantageous embodiment, a method is presented forsecuring a thermal protection element to a structure. A thermalprotection element is positioned with respect to a number of fastenerelements on a surface of a structure. The thermal protection element hasa number of tabs secured to a number of sides on the thermal protectionelement with a number of blind fasteners. The number of blind fastenersis secured to a number of washers within a substrate of the thermalprotection element. The number of tabs is secured to the number offastening elements on the surface of the structure.

In still yet another advantageous embodiment, a method is presented forsecuring a thermal protection element to a structure. The thermalprotection element is positioned with respect to a number of fastenerelements on a surface of a structure. The thermal protection element hasa groove formed in a plurality of sides of the thermal protectionelement and a frame having an inner edge and a number of tabs oppositeof the inner edge. The inner edge of the frame is secured to the groove.The number of tabs is secured to the number of fastener elements on thesurface of the structure.

The features, functions, and advantages can be achieved independently invarious embodiments of the present disclosure or may be combined in yetother embodiments in which further details can be seen with reference tothe following description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features believed characteristic of the advantageousembodiments are set forth in the appended claims. The advantageousembodiments, however, as well as a preferred mode of use, furtherobjectives, and advantages thereof, will best be understood by referenceto the following detailed description of an advantageous embodiment ofthe present disclosure when read in conjunction with the accompanyingdrawings, wherein:

FIG. 1 is a diagram illustrating a spacecraft manufacturing and servicemethod in accordance with an advantageous embodiment;

FIG. 2 is a diagram of a spacecraft in which an advantageous embodimentmay be implemented;

FIG. 3 is a diagram of a thermal protection system in accordance with anadvantageous embodiment;

FIG. 4 is a diagram illustrating a thermal protection system inaccordance with an advantageous embodiment;

FIG. 5 is a diagram of a thermal protection system in accordance with anadvantageous embodiment;

FIG. 6 is a cross-sectional view of a ceramic matrix composite tile inaccordance with an advantageous embodiment;

FIG. 7 is a diagram of a thermal protection system in accordance with anadvantageous embodiment;

FIG. 8 is a partial cross-sectional side view of a thermal protectionelement in accordance with an advantageous embodiment;

FIG. 9 is a diagram illustrating an unassembled frame for a thermalprotection element in accordance with an advantageous embodiment;

FIG. 10 is a magnified view of a portion of a frame in accordance withan advantageous embodiment;

FIG. 11 is a diagram of an assembled frame around a ceramic matrixcomposite tile in accordance with an advantageous embodiment;

FIG. 12 is a magnified view of a portion of an assembled frame on aceramic matrix composite tile in accordance with an advantageousembodiment;

FIG. 13 is a diagram illustrating installation of a frame in accordancewith an advantageous embodiment;

FIG. 14 is a diagram illustrating a magnified portion of a ceramicmatrix composite tile with a frame in accordance with an advantageousembodiment;

FIG. 15 is a diagram illustrating installation of rivets in a frame inaccordance with an advantageous embodiment;

FIG. 16 is a diagram illustrating a completed assembly of a portion of aframe in accordance with an advantageous embodiment;

FIG. 17 is a flowchart of a process for securing a thermal protectionelement to a structure in accordance with an advantageous embodiment;

FIG. 18 is a flowchart of a process for manufacturing a thermalprotection element in accordance with an advantageous embodiment; and

FIG. 19 is a flowchart of a process for manufacturing a thermalprotection element in accordance with an advantageous embodiment.

DETAILED DESCRIPTION

Referring more particularly to the drawings, embodiments of thedisclosure may be described in the context of spacecraft manufacturingand service method 100 as shown in FIG. 1 and spacecraft 200 as shown inFIG. 2. Turning first to FIG. 1, a diagram illustrating a spacecraftmanufacturing and service method is depicted in accordance with anadvantageous embodiment. During pre-production, exemplary spacecraftmanufacturing and service method 100 may include specification anddesign 102 of spacecraft 200 in FIG. 2 and material procurement 104.

During production, component and subassembly manufacturing 106 andsystem integration 108 of spacecraft 200 in FIG. 2 takes place.Thereafter, spacecraft 200 in FIG. 2 may go through certification anddelivery 110 in order to be placed in service 112. While in service by acustomer, spacecraft 200 in FIG. 2 is scheduled for routine maintenanceand service 114, which may include modification, reconfiguration,refurbishment, and other maintenance or service.

Each of the processes of spacecraft manufacturing and service method 100may be performed or carried out by a system integrator, a third party,and/or an operator. In these examples, the operator may be a customer.For the purposes of this description, a system integrator may include,without limitation, any number of spacecraft manufacturers andmajor-system subcontractors; a third party may include, withoutlimitation, any number of venders, subcontractors, and suppliers; and anoperator may be a company, a military entity, a service organization,and so on.

With reference now to FIG. 2, a diagram of a spacecraft is depicted inwhich an advantageous embodiment may be implemented. In thisillustrative example, spacecraft 200 is produced by spacecraftmanufacturing and service method 100 in FIG. 1. Spacecraft 200 mayinclude airframe 202 with a plurality of systems 204 and interior 206.

Examples of plurality of systems 204 include one or more of propulsionsystem 208, electrical system 210, hydraulic system 212, environmentalsystem 214, and thermal protection system 216. At least some of thedifferent advantageous embodiments may provide a method and apparatusfor attaching thermal protection elements within thermal protectionsystem 216 to spacecraft 200. Although an aerospace example is shown,different advantageous embodiments may be applied to other industries,such as the automotive industry.

One or more of the different advantageous embodiments recognize and takeinto account that it is desirable to have a mechanical system forattaching tiles for a thermal protection system to a vehicle structurethat may have less weight. The different advantageous embodiments alsotake into account and recognize that it may be desirable to have amechanical attachment system that may allow for quicker attachment andreplacement of tiles.

The different advantageous embodiments also recognize and take intoaccount that current systems use ceramic tiles that may have ceramicflanges that are fabricated as part of the tile. These ceramic tiles mayinclude, for example, without limitation, ceramic matrix compositewrapped tiles. One or more of the different advantageous embodiments mayrecognize and take into account that these ceramic flanges formed on thetiles may be weaker in carrying loads in certain directions as comparedto other directions.

Advantageous embodiments provide a method and apparatus having a thermalprotection element with an upper surface, a lower surface, and aplurality of sides. A number of washers may or may not be located insidea substrate thermal protection element around a number of sides in theplurality of sides. A number of items, as used herein, refer to one ormore items.

For example, a number of sides are one or more sides. Depending on theparticular implementation, the number of sides may equal the pluralityof sides. A ceramic layer covers at least the plurality of sides of thethermal protection element. A number of fasteners are used to connectthe number of tabs to the number of sides. The fasteners may be securedto the number of washers through holes in the ceramic layer. Thesefasteners may take the form of blind fasteners in these illustrativeexamples.

In some advantageous embodiments, a method and apparatus may be presentin which a thermal protection element has an upper surface, a lowersurface, and a plurality of sides. A groove may be formed in theplurality of sides of the thermal protection element. A frame having aninner edge and a number of tabs opposite to the inner edge may besecured to the groove. The upper and lower surface of the thermalprotection element may be hardened. A “hardened” surface providesincreased durability for a ceramic tile.

The durability may be provided by a layer, such as a ceramic matrixcomposite that may be wrapped around a tile. In other advantageousembodiments, this hardened layer also may be hardened through curing andsintering. Both may be employed in providing hardening for a thermalprotection element. In some advantageous embodiments, the upper andlower surface may include a ceramic matrix composite layer that ishardened along with, or in place of, the ceramic substrate.

With reference now to FIG. 3, a diagram of a thermal protection systemis depicted in accordance with an advantageous embodiment. Thermalprotection system 300 is an example of a thermal protection system suchas, for example, thermal protection system 216 in spacecraft 200 in FIG.2.

In this example, thermal protection system 300 includes thermalprotection element 302. Thermal protection element 302 may be anyelement or structure capable of providing thermal protection. In otherwords, thermal protection element 302 may protect a surface from heatand/or cold. Thermal protection element 302 may take the form of ceramicmatrix composite tile 304. Of course, thermal protection element 302 mayalso be implemented using other types of ceramics or materials,depending on the particular implementation. Thermal protection element302 may be comprised of a single substrate, layers of materials, blendsof materials, or some other suitable material or combination ofmaterials.

In these illustrative examples, thermal protection element 302 may havesubstrate 312 and facesheet 314. Facesheet 314 is a layer of materialthat may cover substrate 312. This layer of material may be a singlelayer and/or a laminate. Substrate 312 may be comprised of a singlematerial or multiple materials, and/or may have layers or differentstructures or substructures. Facesheet 314 may be made of ceramic, aceramic matrix composite material, and/or some other suitable material.Facesheet 314 may be used to provide a strengthened exterior that mayincrease damage resistance to impacts that may occur.

Thermal protection element 302 may have upper surface 306 opposite oflower surface 308. Sides 310 are located between upper surface 306 andlower surface 308. In these illustrative examples, cavities 316 arelocated within sides 310 under facesheet 314. Washers 318 may be locatedwithin cavities 316 in these examples. Washers 318 also may be comprisedof a ceramic matrix composite material.

Facesheet 314 has holes 320, which may be in communication with washers318 and cavities 316. In these examples, blind fasteners 322 may securetabs 324 to thermal protection element 302. More specifically, blindfasteners 322 may be secured to washers 318 and facesheet 314 in theseillustrative examples. Blind fasteners 322 may be placed through holes320, washers 318, holes 326 in tabs 324 and secured. Washers 318 may beunnecessary if facesheet 314 has sufficient rigidity to allow tabs 324to be secured in holes 326 using blind fasteners 322.

In these examples, blind fasteners 322 may be, for example, blindrivets. Of course, any fastener may be used that may be capable of beingfastened when only one side of the object is accessible for securing afastener.

Tabs 324, with or without holes 328, are capable of being secured tofastening elements 330 secured to surface 332 of structure 334.Fastening elements 330 may take various forms. For example, fasteningelements 330 may be posts 336 secured to surface 332 of structure 334.Structure 334 may take various forms. For example, structure 334 may bea structural element on which a skin of the spacecraft is secured.

Next, in FIG. 4, a diagram illustrating a thermal protection system isdepicted in accordance with an advantageous embodiment. Thermalprotection system 400 is an example of a thermal protection system suchas, for example, thermal protection system 216 for spacecraft 200 inFIG. 2.

In this example, thermal protection system 400 may include thermalprotection element 402. Thermal protection element 402 may be, forexample, ceramic matrix composite tile 404. Ceramic matrix compositetile 404 may be substrate 406 that is wrapped with facesheet 408.Facesheet 408 may be wrapped around substrate 406 and cured and sinteredto form ceramic matrix composite tile 404. Substrate 406 may be, forexample, without limitation, a ceramic material and/or some othersuitable material. Facesheet 408 may be, for example, withoutlimitation, a ceramic matrix composite. Thermal protection element 402may be comprised of substrate 406 and facesheet 408.

Thermal protection element 402 has upper surface 410 opposite of lowersurface 412. Sides 414 are located between upper surface 410 and lowersurface 412. Facesheet 408 may cover at least a portion of thermalprotection element 402.

In this illustrative example, groove 416 is formed in sides 414. Frame418 has inner edge 420 and tabs 422. Inner edge 420 is configured toengage groove 416 when frame 418 is secured to thermal protectionelement 402.

Facesheet 408 may conform to groove 416, and inner edge 420 may engagefacesheet 408 in groove 416. Tabs 422 are located opposite of inner edge420. Frame 418 may be formed from rails 424, 426, 428, and 430. Theserails may be joined to secure frame 418 to groove 416. Rails 424, 426,428, and 430 may use fasteners 432 and brackets 434. Frame 418 may besecured to groove 416 with a compressive load.

Thermal protection element 402 may be secured to surface 436 ofstructure 438 by securing tabs 422 to fastening elements 440 located onsurface 436 of structure 438. Structure 438 may be, for example, astructural element on a spacecraft. Fastening elements 440 may be, forexample, posts 442. Tabs 422 are configured such that they can besecured to posts 442 in these examples.

In this manner, the thermal protection systems illustrated in FIGS. 3and 4 may provide a capability to attach thermal protection elements toa surface of a structure in a manner that reduces the weight of asystem. For example, the different advantageous embodiments may notrequire a carrier plate to mount the tile. Instead, the differentadvantageous embodiments provide mounting structures for the thermalprotection elements.

The illustrations of thermal protection system 300 in FIG. 3 and thermalprotection system 400 in FIG. 4 are not meant to imply physical orarchitectural limitations to the manner in which different advantageousembodiments may be implemented. Other components may be used in additionto, or in place of, the ones illustrated in some advantageousembodiments. In yet other advantageous embodiments, some of theillustrated components may be unnecessary.

For example, in some advantageous embodiments, posts 336 and posts 442may be unnecessary. Instead, tabs 324 and tabs 422 may be secureddirectly to surface 332 of structure 334 and surface 436 of structure438 using a fastener. In yet other advantageous embodiments, the thermalprotection system may include additional thermal protection elementsrather than the single ones illustrated for each thermal protectionsystem. In still other advantageous embodiments, the thermal protectionelements may be made of other types of materials other than a ceramicmatrix composite, including, for example, without limitation, metalmatrix composites and monolithic ceramics. As a further example, somesubstrates may have additional cavities or may be hollow.

The different fastening components such as, for example, withoutlimitation, tabs, frames, washers, blind fasteners, and other suitablecomponents may be made of various materials. In these differentillustrative examples, these components may be made of a monolithiccomposite, ceramic composite, and/or a metal. The metal may be, forexample, without limitation, titanium, steel, high temperature alloys,and/or some other metal suitable for use with thermal protectionsystems. When selecting materials for this system, the compatibility ofcoefficients of thermal expansion (CTEs) and temperature limitations forthe different materials may be considered.

With reference now to FIG. 5, a diagram of a thermal protection systemis depicted in accordance with an advantageous embodiment. In thisillustrative example, thermal protection system 500 is an example of oneimplementation for thermal protection system 300 in FIG. 3. In thisillustrative example, thermal protection element 502 takes the form ofceramic matrix composite tile 504.

In this example, ceramic matrix composite tile 504 has upper surface 506and lower surface 508. Sides 510, 512, 514, and 516 are present betweenupper surface 506 and lower surface 508. These sides and/or surfaces maynot be parallel or substantially parallel to each other depending on theshape of the ceramic matrix composite tile. In this illustrativeexample, lower surface 508 of ceramic matrix composite tile 504 issecured to surface 518 of structure 520.

Tabs 522 and 524 are attached to side 510, while tabs 526 and 528 areattached to side 512. Additional tabs are present on sides 514 and 516but are not seen in this view. These tabs may be secured to ceramicmatrix composite tile 504 using blind rivets and washers. Posts 540-546are secured to surface 518 of structure 520 in this view. Tabs 522-528may be secured to posts 540-546. In these illustrative examples, thetabs and posts may be made of stainless steel and/or titanium.

With reference now to FIG. 6, a cross-sectional view of a ceramic matrixcomposite tile is depicted in accordance with an advantageousembodiment. In this example, a partial cross-sectional view of ceramicmatrix composite tile 504 is depicted in accordance with an advantageousembodiment. This cross-sectional view is taken along lines 6-6 in FIG.5.

In this partial cross-sectional view, ceramic matrix composite tile 504is comprised of substrate 600 and facesheet 602. Substrate 600 may becomprised of a ceramic material. Facesheet 602 may be comprised of aceramic composite material. In some advantageous embodiments, substrate600 also may be comprised of a ceramic matrix composite material and, insome embodiments, facesheet 602 may be comprised of a ceramic material.Of course, any material suitable for use in protecting a surface againstheat may be used.

Additionally, substrate 600 has cavity 604 formed within substrate 600.Cavity 604 may be formed when ceramic matrix composite tile 504 isformed. In other advantageous embodiments, cavity 604 may be drilledand/or bored out of side 512. Washer 606 is located within cavity 604 oninner side 608 of facesheet 602. Cavity 604 may have a configuration andsize to contain washer 606 and have additional clearance to receiveblind rivet 610. Washer 606 also may be comprised of a ceramic matrixcomposite material. Washer 606 may be placed within cavity 604 andfacesheet 602 placed over substrate 600. Washer 606 and facesheet 602may be cured to form ceramic matrix composite tile 504.

In the illustrative example, washer 606 may be made from a ceramicmatrix composite. Washer 606 may be around ⅝ inches in diameter andaround ⅛ inch thick in this example. Of course, other dimensions may beused, depending on the particular implementation. Cavity 604 may bemachined to the same depth as washer 606 with a slightly larger diameterto allow for installation of washer 606.

Facesheet 602 may be formed from around four plies of a ceramic matrixcomposite material. Facesheet 602 may be around 0.040 inches thick inthese examples. Of course, other thicknesses and numbers of plies may beused, depending on the particular implementation.

Blind rivet 610 may be placed through hole 612 in tab 528 and throughwasher 606 to secure tab 528 to thermal protection element 502. Blindrivet 610 may be made of various materials. For example, withoutlimitation, blind rivet 610 may be made of steel, titanium, ahigh-temperature alloy, and/or some other suitable material. In thisillustrative example, tab 528 is capable of being secured to post 544.

In this illustrative example, tab 528 may be secured to post 544 usingnut 616. Post 544 may be coupled to hole 614 in tab 528. By securing tab528 to post 544, thermal protection element 502 may be secured tostructure 520. In these illustrative examples, a composi-loc II rivetmay be used. This rivet may be available from Monogram AerospaceFasteners Company. Of course, any type of rivet may be used for blindrivet 610 that may have a controlled pre-load that does not crush washer606 and facesheet 602.

Although washer 606 is illustrated in these examples, washer 606 may beunnecessary in some advantageous embodiments. If facesheet 602 hassufficient strength to hold blind rivet 610 and tab 528, washer 606 maybe omitted. With this type of implementation, locations in which blindfasteners are to be secured to facesheet 602 may be reinforced. Forexample, these locations may be reinforced using a material such as, forexample, a ceramic matrix composite material, a ceramic, a metal, and/orsome other suitable material. Further, in some advantageous embodiments,both washers and reinforcements of facesheet 602 may be used.

With reference now to FIG. 7, a diagram of a thermal protection systemis depicted in accordance with an advantageous embodiment. Thermalprotection system 700 is an example of one implementation of thermalprotection system 400 in FIG. 4. In this illustrative example, thermalprotection element 702 may take the form of ceramic matrix compositetile 704.

Ceramic matrix composite tile 704 has upper surface 706 and lowersurface 708. Additionally, ceramic matrix composite tile 704 has sides710, 712, 714, and 716. Lower surface 708 may be secured to surface 718of structure 720. Frame 722 is secured to sides 710, 712, 714, and 716.Frame 722 may be constructed from various materials. For example,without limitation, frame 722 may be constructed from titanium.

Frame 722 has tabs 724, 726, 728, and 730. Tabs 724 and 726 are locatedon side 712, while tabs 728 and 730 are located on side 714. Additionaltabs are present on frame 722 on sides 710 and 716 but not seen in thisview.

Posts 732, 734, 736, and 738 are secured to surface 718 of structure720. Tabs 724, 726, 728, and 730 may be secured to posts 732, 734, 736,and 738, respectively.

With reference now to FIG. 8, a partial cross-sectional side view of athermal protection element is depicted in accordance with anadvantageous embodiment. In this example, the partial cross-sectionalside view is taken along lines 8-8 in FIG. 7. In this example, thermalprotection element 702 has substrate 800 and facesheet 802. As can beseen in this example, inner edge 804 of frame 722 fits into groove 806in thermal protection element 702.

In this example, groove 806 is substantially cylindrical, and inner edge804 has a cylindrical shape that fits within groove 806. Thiscylindrical shape may reduce shear and tension on facesheet 802. Ofcourse, other shapes for inner edge 804 and groove 806 may be used,depending on the particular implementation.

Turning to FIG. 9, a diagram illustrating an unassembled frame for athermal protection element is depicted in accordance with anadvantageous embodiment. In this example, thermal protection element 900takes the form of ceramic matrix composite tile 902. Ceramic matrixcomposite tile 902 has lower surface 904 and upper surface 906. In thisillustrative example, ceramic matrix composite tile 902 is shown in anupside down view with lower surface 904 facing upwards. Ceramic matrixcomposite tile 902 also has sides 908, 910, 912, and 914 located betweenlower surface 904 and upper surface 906. Groove 916 is formed alongsides 908, 910, 912, and 914.

In this example, frame 918 is comprised of rails 920, 922, 924, and 926.Rails 920 and 922 are joined to each other by bracket 928, while rail924 and rail 926 are joined to each other by bracket 930. Rail 920 hastabs 932 and 934 with holes 936 and 938. Rail 922 has tabs 940 and 942with holes 944 and 946. Rail 924 has tabs 948 and 950 with holes 952 and954. Rail 926 has tabs 956 and 958 with holes 960 and 962.

With reference to FIG. 10, a magnified view of a portion of a frame isdepicted in accordance with an advantageous embodiment. In thisillustrative example, a more detailed view of section 964 from FIG. 9 isillustrated.

As can be seen in this illustration, rail 924 and rail 926 of frame 918have inner edge 1000 and inner edge 1002. Rail 924 is secured to rail926 through bracket 930. Rivets 1004, 1006, 1008, and 1010 are used tosecure rails 926 and 924 to bracket 930.

In FIG. 11, a diagram of an assembled frame around a ceramic matrixcomposite tile is depicted in accordance with an advantageousembodiment.

With reference to FIG. 12, a magnified view of a portion of an assembledframe on a ceramic matrix composite tile is depicted in accordance withan advantageous embodiment. In this example, a more detailed view ofsection 1100 in FIG. 11 is illustrated.

As can be seen in this view, screw 1200 may be placed into frame 918 topre-load or put a compressive load on ceramic matrix composite tile 902.In this manner, frame 918 may place a compressive pre-load on ceramicmatrix composite tile 902.

With reference now to FIG. 13, a diagram illustrating installation of aframe is depicted in accordance with an advantageous embodiment. In thisexample, blocks 1300 and 1302 may be placed on sides 1304 and 1306 ofceramic matrix composite tile 1308 with frame 1310 in place. Gripmechanism 1312 may hold blocks 1302 and 1304 in place. Section 1314 isshown in more detail in FIG. 14 below.

Next, in FIG. 14, a diagram illustrating a magnified portion of aceramic matrix composite tile with a frame is depicted in accordancewith an advantageous embodiment. In this more detailed view of section1314, clevis 1400 may be attached to rail 1402 of frame 1310 by pin1404. Screw 1406 may turn and place pressure on block 1300 in a mannerthat induces a tensile load on frame 1310 and a compressive load onceramic matrix composite tile 1308. Screw 1408 may be used to securerail 1402 to rail 1410. Screw 1408 also may be used to create a tensileload on frame 1310 and a compressive load on ceramic matrix compositetile 1308.

Next, in FIG. 15, a diagram illustrating installation of rivets in aframe is depicted in accordance with an advantageous embodiment. In thisexample, rivets 1500 and 1502 may be installed after rail 1402 has beenaligned with rail 1410 with the desired amount of force.

With reference now to FIG. 16, a diagram illustrating a completedassembly of a portion of a frame is depicted in accordance with anadvantageous embodiment. In this example, after rivets 1500 and 1502have been installed, clevis 1400 (not shown) and block 1300 (not shown)may be removed. Thereafter, rivets 1600 and 1602 may be installed andscrew 1408 removed to complete installation or securing of rail 1402 torail 1410.

Turning now to FIG. 17, a flowchart of a process for securing a thermalprotection element to a structure is depicted in accordance with anadvantageous embodiment. This process may be implemented using thermalprotection system 300 in FIG. 3 or thermal protection system 400 in FIG.4.

The process begins by positioning the thermal protection element withthe tabs over a surface of a structure (operation 1700). The thermalprotection element may be, for example, thermal protection element 302in FIG. 3. The tabs may be secured to fastening elements on the surfaceof the structure (operation 1702), with the process terminatingthereafter.

With reference now to FIG. 18, a flowchart of a process formanufacturing a thermal protection element is depicted in accordancewith an advantageous embodiment. The process illustrated in FIG. 18 maybe used to manufacture a thermal protection element such as, forexample, thermal protection element 302 in FIG. 3.

The process begins by forming a substrate for the thermal protectionelement (operation 1800). Next, cavities are formed in the sides of thesubstrate (operation 1802). These cavities may be formed by drillingand/or machining in these examples. Washers are placed into the cavities(operation 1804). These washers may be constructed from ceramic matrixcomposite laminates.

A ceramic layer is placed around the substrate (operation 1806). Thislayer may be formed from a ceramic matrix composite material. The layermay be a facesheet or a ceramic layer for the thermal protectionelement. The covered substrate is cured and sintered (operation 1808).This curing may be performed in an autoclave, depending on theparticular implementation. The sintering may be performed in a furnace.

Holes are drilled through the facesheet that are aligned with holes inthe washers (operation 1810). Metal tabs are riveted to the tile usingthe washers in the thermal protection element (operation 1812), with theprocess terminating thereafter.

With reference now to FIG. 19, a flowchart of a process formanufacturing a thermal protection element is depicted in accordancewith an advantageous embodiment. The process illustrated in FIG. 19 maybe implemented to manufacture a thermal protection element such as, forexample, thermal protection element 402 in FIG. 4.

The process begins by forming a substrate for the thermal protectionelement (operation 1900). The process then forms a groove in the sidesof the substrate (operation 1902). The groove may be machined or milledinto the sides of the substrate. A facesheet may then be formed aroundthe substrate (operation 1904). For example, the facesheet may be aceramic matrix composite layer wrapped around the substrate.

The ceramic matrix composite layer may then be cured and sintered. Theprocess assembles rails into half sections with rivets and brackets(operation 1906). In this example, each half section may be formed fromtwo rails and a bracket. The half sections of the frame are aligned withthe grooves (operation 1908). The half sections are then secured to eachother (operation 1910).

Reaction blocks are mounted with a clamp and clevis as pull assemblies(operation 1912). Screws are tightened to create an even compressionload on the sides of the thermal protection element (operation 1914).Holes are drilled and rivets are placed into the corners of the halfsections to secure the frame (operation 1916). The clevis assemblies,reaction blocks, and screws are then removed (operation 1918), with theprocess terminating thereafter. The screws are no longer needed afterthe rivets are put in place.

The flowcharts and block diagrams in the different depicted embodimentsillustrate the architecture, functionality, and operation of somepossible implementations of apparatus and methods. In this regard, eachblock in the flowchart or block diagrams may represent a module,segment, operation, or portion of a component or process forimplementing the specified number of functions and/or components. Insome alternative implementations, the function or functions noted in theblocks may occur out of the order noted in the figures. For example, insome cases, two blocks shown in succession may be executed substantiallyconcurrently, or the blocks may sometimes be executed in the reverseorder, depending upon the functionality involved.

Thus, one or more of the different advantageous embodiments provide amethod and apparatus for a thermal protection system. In the differentillustrative examples, a thermal protection element is mechanicallysecured to a surface of a structure. In some of the illustrativeexamples, tabs are secured to the thermal protection element usingwashers located inside of the thermal protection element. In otheradvantageous embodiments, a rail with tabs is secured to a groove aroundthe thermal protection element. One or more of the differentadvantageous embodiments may provide increased durability orload-bearing capability as compared to currently used ceramic tabs thatare formed integrally as part of a ceramic tile.

With one or more of the different advantageous embodiments, a carrierplate may become unnecessary for mounting the thermal protection elementto the surface of the structure. The different advantageous embodimentsprovide mounting elements, such as tabs, either secured to the thermalprotection element through fasteners and/or rails for use in securingthe thermal protection element to the surface of the structure.

Further, these different attachment mechanisms, as illustrated in theexamples, may facilitate faster replacement of thermal protectionelements as compared to currently available systems. Further, the tabsare able to withstand additional force normal to the tile as compared tocurrently used ceramic tabs formed integrally with a tile. For example,in some advantageous embodiments, the tabs are capable of carryingaround 30 to around 50 pounds per linear inch of vertical load beforefailure.

The description of the different advantageous embodiments has beenpresented for purposes of illustration and description, and it is notintended to be exhaustive or limited to the embodiments in the formdisclosed. Many modifications and variations will be apparent to thoseof ordinary skill in the art. Although the different advantageousembodiments have been described with respect to spacecraft, otheradvantageous embodiments may be applied to other types of objects.

For example, without limitation, other advantageous embodiments may beapplied to a mobile platform, a stationary platform, a land-basedstructure, an aquatic-based structure, a space-based structure, and/orsome other suitable object. More specifically, the differentadvantageous embodiments may be applied to, for example, withoutlimitation, a spacecraft, a satellite, a space station, a rocket, anaircraft, a rover, an automobile, an engine, an engine structure, abuilding, and/or some other suitable object.

Further, different advantageous embodiments may provide differentadvantages as compared to other advantageous embodiments. The embodimentor embodiments selected are chosen and described in order to bestexplain the principles of the embodiments, the practical application,and to enable others of ordinary skill in the art to understand thedisclosure for various embodiments with various modifications as aresuited to the particular use contemplated.

What is claimed is:
 1. An apparatus comprising: a thermal protection element having an upper surface, a lower surface, and a plurality of sides, each of the plurality of sides having an outside, the thermal protection element comprising a ceramic substrate and a facesheet, the facesheet comprising a ceramic layer, the ceramic layer covering the upper surface, the lower surface, and the plurality of sides of the thermal protection element, a number of cavities in the ceramic substrate and a number of holes in the facesheet; a number of blind fasteners positioned such that a portion of the number of blind fasteners extends through the number of holes in the facesheet and into the number of cavities in the ceramic substrate; a number of first portions of a number of tabs, each of the number of first portions affixed to the outside of the plurality of sides by the number of blind fasteners secured to the ceramic layer, wherein each of the number of tabs have a second portion extending substantially perpendicularly away from the plurality of sides and substantially parallel to and at a distance above a structure; and a number of fastening elements each having a first end secured to the structure and a second end secured to the second portion and interposed between the structure and the second portion for the distance to create a space between the structure and the second portion; wherein the lower surface is secured to the structure by the number of tabs, the number of blind fasteners, and the number of fastening elements.
 2. The apparatus of claim 1 further comprising: a number of washers located inside the number of cavities in the substrate of the thermal protection element around a number of sides in the plurality of sides, wherein the number of tabs is connected to the number of sides by the number of blind fasteners secured to the number of washers and the ceramic layer.
 3. The apparatus of claim 2, wherein the number of washers is comprised of a material selected from one of a ceramic matrix composite material, a ceramic material, and a metal.
 4. The apparatus of claim 1, wherein the thermal protection element is a ceramic tile.
 5. The apparatus of claim 1, wherein the structure is for an object selected from one of a mobile platform, an aircraft, a tank, a personnel carrier, a train, a spacecraft, a submarine, a satellite, a rocket, an engine, an engine structure, and an automobile.
 6. The apparatus of claim 1, wherein the ceramic layer is reinforced at a number of locations on which the number of tabs is connected to the plurality of sides by the number of blind fasteners secured to the ceramic layer.
 7. The apparatus of claim 6, wherein the number of locations are reinforced using a material selected from one of a ceramic matrix composite material, a ceramic, and a metal.
 8. The apparatus of claim 1 wherein the number of tabs and the number of fastening elements comprise stainless steel or titanium.
 9. A method for securing a thermal protection element to a structure, the method comprising: forming a facesheet over a substrate, the facesheet and the substrate comprising ceramic materials, the facesheet covering an upper surface, lower surface, and a number of sides of the substrate, the facesheet and substrate comprising a thermal protection element; forming a number of cavities in the substrate and forming a number of holes in the facesheet; positioning a number of washers in the number of cavities such that a surface of the number of washers is adjacent to an inner surface of the facesheet; positioning a number of blind fasteners through the number of holes with a portion of the number of blind fasteners positioned in the number of cavities; connecting a first end of a number of fastening elements to the structure; positioning the thermal protection element with respect to the number of fastening elements on a surface of the structure, wherein the thermal protection element has a number of first portions of a number of tabs secured to a number of sides on the thermal protection element by a number of blind fasteners, wherein each of the number of tabs have a second portion extending substantially perpendicularly away from the number of sides and substantially parallel to and at a distance above a structure; and securing the second portion of each of the number of tabs to a second end of each of the number of fastening elements so that each of the number of fastening elements is interposed between the structure and the second portion for the distance to create a space between the structure and the second portion; wherein the thermal protection element is secured to the structure by the number of tabs, the number of blind fasteners, and the number of fastening elements.
 10. The method of claim 9 further comprising: forming the substrate for the thermal protection element from a ceramic matrix composite material; forming the first number of holes in the facesheet, wherein the first number of holes is aligned with a second number of holes in the number of washers; and attaching the number of tabs to the number of sides on the thermal protection element with the number of blind fasteners secured to the number of washers within the substrate of the thermal protection element.
 11. The method of claim 10 further comprising: placing the number of washers within the number of cavities before forming the facesheet over the substrate.
 12. The method of claim 10, wherein the number of blind fasteners are secured to the facesheet for the thermal protection element and to the number of washers in the substrate.
 13. The method of claim 9 wherein the number of fastening elements comprise a number of posts. 